Segmented electrode hall thruster

Kevin D. Diamant, James E. Pollard, Ronald B. Cohen, Yevgeny Raitses, Nathaniel J. Fisch

Research output: Contribution to journalArticle

12 Scopus citations

Abstract

Thrust, thrust efficiency, and plume divergence were measured for a 9 cm diam laboratory model Hall thruster with segmented electrodes in the discharge channel. Several geometries with graphite nonemissive electrodes, and one with a tungsten emissive electrode were tested and compared to a baseline configuration with all electrodes replaced by boron nitride segments. To within measurement uncertainty, thrust and thrust efficiency were unaffected by insertion of electrodes, with the exception of reduced efficiency for a configuration which resulted in a 20% increase in discharge current. Maximum plume half-angle reductions of 4 deg were obtained with emissive and nonemissive electrodes.

Original languageEnglish (US)
Pages (from-to)1396-1401
Number of pages6
JournalJournal of Propulsion and Power
Volume22
Issue number6
DOIs
StatePublished - 2006

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Fuel Technology
  • Mechanical Engineering
  • Space and Planetary Science

Fingerprint Dive into the research topics of 'Segmented electrode hall thruster'. Together they form a unique fingerprint.

  • Cite this

    Diamant, K. D., Pollard, J. E., Cohen, R. B., Raitses, Y., & Fisch, N. J. (2006). Segmented electrode hall thruster. Journal of Propulsion and Power, 22(6), 1396-1401. https://doi.org/10.2514/1.19417